Vtol box-wing multirotor aerial vehicle

ABSTRACT

A VTOL (vertical take-off and landing) box-wing aerial vehicle with multirotor to provide VTOL flight includes a detachable cabin, centered fuselage, a pair of first wings extending outward from the upper portion of the fuselage and a pair of second wings extending outwardly and from the lower portion of the fuselage. The first and second wings are spaced apart longitudinally and vertically. The pylon joints the first wing and second wing at the tip to form the box-wing. The pylon includes heading control rudder. Secured to the wing or pylon or both wing and pylon, an overhead boom extending longitudinally to support a plurality of lift rotors or tiltable rotors for VTOL flight. Finally, the fuselage mounted push rotor or the overhead boom mounted tiltable rotors propel the vehicle forward to generate lift from the wings. Furthermore, the wings are equipped with elevators and ailerons for flight control.

CROSS-REFERENCE TO RELATED APPLICATIONS

U.S. PATENT DOCUMENTS 3,053,480 Oct. 6 1959 Edward G. Vanderlip 2443,834,654 Sep. 10 1974 Luis R. Miranda 244/14 5,503,352 Apr. 2 1996Vladimir S. Eger 244/45 2018/0305005 Oct. 25,2018 Robert W. Park B64C27/26 B64C 27/30 B64C 29/0025 B64D 27/24 10,364,036 B6 Jul. 30,2019James Joseph Tigh B64C 29/02 B64C 29/00 B64C 29/005 2020/0317353 A1 Oct.8, 2020 JoeBen Bevirt B64D 27/24 B64C 29/0033 B64C 39/068 B64C 29/0033B64C 39/068 10,981,650 B2 Apr. 20,2021 Axel Fink, D B64C 39/068 B64C29/0025 10,994,829 B2 May 4,2021 Michael J. Duffy B64C 2201/108 B64C2201/104 B64C 2201/024

FOREING PATENT DOCUMENTS EP3098161B1 May 24, 2016 Judas, Micheal B64C29/00

BACKGROUND ON INVENTION 1. Field of the Invention

The disclosed invention relates to a VTOL (vertical take-off andlanding) box-wing aerial vehicle, and more specifically to theconfiguration of the box-wing airframe configurated with multiple rotarywings for VTOL flight and the tiltable rotor or push rotor for forwardflight.

2. Discussion of the State of the Art

The helicopter is an essential modern air transportation vehicle.Technically, helicopter with rotary wing is also referred as“rotorcraft” or “rotary wing vehicle”. The rotary wing is commonlyreferred as “rotor”. Rotary wing positioned in the center of a shroud iscalled “ducted fan”. In general, rotary wing consists of propellercomprising of a plurality of blades. The rotary movement of the bladesworks as the air mover to generate thrust. The rotary wing permits thehelicopter to land and take-off vertically without the presence of along run way. Disadvantageously, helicopter with fossil fuel engine isassociated with expensive operational cost, undesirable high level ofnoise and carbon emission.

As the traffic is increasing heavy in the global urban area, anaffordable electrical VTOL vehicle is the solution to avoid thecongestion on the road. Without traffic delay, an electrical VTOLvehicle can also operate as law enforcement vehicle, ambulance andmedical cargo transporter. A new term UAM (urban air mobility) isadopted for this new type of aerial transportation.

Modern electrical VTOL vehicle with multiple rotary wings is known asmultirotor vehicle. The multiple rotary wing system provides an agilesteering capability. The energy required for VTOL flight issignificantly higher than the energy required for a fix wing airplane tomaintain forward flight. Advantageously, modern electrical VTOL vehiclealso has the capability to transition to airplane mode for forwardflight. During forward flight, the VTOL vehicle is depending on theforward speed to generate lift from the fixed wings. Furthermore, thepropulsive movement is generated by a push rotor or tiltable rotor.

Traditional fixed wing aircraft suffers from significant loses of liftefficiency at the tip of the wings, due to the occurrence of vortex. Asa result, winglet, sharklet and box-wing design is introduced to improvelift efficiency.

A bigger challenge for VTOL vehicle to operates safety near the ground,by maintaining safe distance between the rotating blade and the personor object.

BRIEF SUMMARY OF THE INVENTION

In one embodiment of the invention a box-wing multirotor vehicle withboth VTOL and airplane forward flight capability is provided, comprisinga detachable cabin, a fuselage base having a longitudinal axis, fixedwings having a biplane arrangement, a pylon secured to the fixed wingsat the tip, a pair of rudder, a pair of overhead boom, a pair of forwardcontra-rotating lift rotor, an tiltable lift and push rotormechanically, a main landing gear pad or wheel, a horizontal andvertical stabilizer, a yaw servo tail boom, a rear contra-rotating liftrotor, and a nose landing gear pad or wheel.

Also in one embodiment the detachable cabin is separable from thebox-wing multirotor vehicle for ground transportation. Also in oneembodiment an overhead boom comprising of a plurality of lift rotorsfrom the forward to the rear portion. Also in one embodiment the forwardcontra-rotating lift rotors and rear contra-rotating lift rotor exertfirstly the lift needed for take-off, for landing, for hovering, and forflying vertically. Also in one embodiment the yaw servo tail boomdirects thrust sideway to provide a complimentary control of the yawheading. Also in one embodiment the tiltable lift and push rotor aimingin the downward position exerts complimentary lift needed for take-off,for landing, for hovering, for flying vertically. Also in one embodimentthe tiltable lift and push rotor aiming in the aftward position providesthe propulsive force for forward motion. Also in one embodiment thefixed wings provide the lift to the vehicle during forward flight. Alsoin one embodiment the rudder, elevator and aileron provide pitch, rolland yaw control during forward flight. Also in one embodiment the fixedwings can have a triplane arrangement.

In another embodiment of the invention a box-wing multirotor vehiclewith both VTOL and airplane forward flight capability is provided,comprising a detachable cabin, a fuselage base having a longitudinalaxis, fixed wings having a biplane arrangement, a pylon secured thefixed wings at the tip, a pair of rudder, a pair of overhead boom, apair of forward contra-rotating lift rotor, a pair of rearcontra-rotating lift rotor, a main landing gear pad or wheel, ahorizontal and vertical stabilizer, a push rotor, and a nose landinggear pad or wheel.

Also in one embodiment the detachable cabin is separable from thebox-wing multirotor vehicle for ground transportation. Also in oneembodiment the overhead boom comprising of a plurality of lift rotorsfrom the forward to the rear portion. Also in one embodiment the forwardcontra-rotating lift rotor and rear contra-rotating lift rotor exertfirstly the lift needed for take-off, for landing, for hovering, and forflying vertically. Also in one embodiment the push rotor provides thepropulsive force for forward motion. Also in one embodiment the fixedwings provide the lift for the vehicle during forward flight. Also inone embodiment the rudder, the elevator and aileron provide pitch, rolland yaw control during forward flight. Also in one embodiment the fixedwings can have a triplane arrangement.

BRIEF DESCRIPTION OF THE DRAWINGS

Regarding the invention disclosure, the feature and advantage of theinvention are particularly pointed and distinctly claimed in the claims.Detailed description and methods are given to provide furthercomprehension of the functionality of the invention. It should beobserved that three mutual orthogonal directions X, Y, and Z are shownin some of the FIGURES. The first direction X is said to be“longitudinal”, and the forward side is referenced to be positive.Rotational movement around the longitudinal axis is said to be “roll”.The second direction Y is said to be “transverse”, and the port side isreferenced to be positive. And the Y plane is referenced as centerlineof the vehicle. Rotational movement around the transverse axis is saidto be “pitch”. Finally, the third direction Z is said to be “vertical”,and the up side is referenced to be positive. Rotational movement aroundthe vertical axis is said to be “yaw”. Furthermore, the direction ofmotion is shown in dash arrow and axis of rotation is shown in dot dashline.

FIG. 1 is a perspective view of box-wing multirotor vehicle in forwardflight configuration according to an embodiment of the presentinvention.

FIG. 2 is a side view of the box-wing multirotor vehicle of FIG. 1 .

FIG. 3 is a top plan view of the box-wing multirotor vehicle of FIG. 1 .

FIG. 4 is a frontal view of the box-wing multirotor of FIG. 1 .

FIG. 5 is a side view of the embodiment of box-wing multirotor vehicledepicting the VTOL configuration.

FIG. 6 is a side view of the embodiment of box-wing multirotor vehicledepicting the operation of the yaw servo tail boom.

FIG. 7 is a side view of the embodiment of the box-wing multirotorvehicle depicting the capability of separating the cabin from thefuselage base.

FIG. 8 is a perspective view of box-wing multirotor vehicle inalternative configuration according to a further embodiment of thepresent invention.

FIG. 9 is a side view of the box-wing multirotor vehicle of FIG. 8 .

FIG. 10 is a plan view of the box-wing multirotor vehicle of FIG. 8 .

DETAILED DESCRIPTION OF THE EMBODIMENTS

Advantageously, VTOL (vertical take-off and landing) vehicle can operatewithout a long runway. However, VTOL operation requires significantlyhigher energy than the energy required for a fixed wing aircraft tomaintain forward flight. Therefore, the usefulness of VTOL vehicle islimited to short range flight. Modern VTOL is commonly designed withelectrical power plant. In order to reduce the weight of electricalenergy storage, an efficient VTOL vehicle can adapt to airplane mode forlong range forward fight. In the disclosure of the invention, thetechnical term rotary wing is referred as “rotor”, and a rotary wingdedicated to generate lift is referred as “lift rotor”.

FIGS. 1 to 4 shows the embodiment of the present invention in forwardflight configuration. FIG. 2 shows a side view of the embodiment. Theaerial vehicle is shown in the usual way, the fuselage of the box-wingmultirotor vehicle 100 comprises of a detachable cabin 101 and thefuselage base 102. The upper portion of the fuselage base 102 isprovided with upper wing 103 and the lower portion of the fuselage base102 is provided with lower wing 104. (Reference to FIG. 3 ) The upperwing 103 and lower wing 104 are joint at the tip by the pylon 105 toform the box-wing structure. The pylon 105 is provided with a headingcontrol rudder 106. On the upper portion of the pylon 105 is providedwith the overhead boom 107. On the lower portion of the pylon 105 isprovided with the main landing gear pad 108. It can also be landingwheel. The forward portion of the overhead boom 107 is provided with theforward contra-rotating lift rotor, which comprises of the forward upperlift rotor 109 and forward lower lift rotor 110, and it may possibly beducted fan. The rear portion of the overhead boom 107 is provided withthe tiltable lift and push rotor 111, and it may possibly be ducted fan.In the rear portion of the fuselage base 102 is provided with thehorizontal and vertical stabilizer 112. At the tail of the fuselage base102 is provided with the yaw servo tail boom 113. The yaw servo tailboom 113 is provided with the rear contra-rotating lift rotor, whichcomprises of rear upper lift rotor 114 and rear lower lift rotor 115,and it may possibly be ducted fan. At the nose portion of the fuselagebase 102 is provided with nose landing gear pad 116. It can also belanding wheel.

FIG. 3 shows the plane view of the embodiment. The wings of the box-wingmultirotor vehicle 100 comprises of the articulated upper wing 103sweeps forward from the top portion of the fuselage base 102. The upperwing 103 is provided with elevator 117. The articulated lower wing 104sweeps aftward from the lower portion of the fuselage base 102. Thelower wing 104 is provided with aileron 118. The wing can also bedihedral or anhedral. The opposite sweeps of the upper wing 103 andlower wing 104 permits optimum advantages of uniform air flow around thetwo main wings.

FIG. 4 shows the front view of the embodiment. It can be observed thatthe following components of the box-wing multirotor vehicle 100 areduplicated and symmetrical located on opposing sides of the Y plane.These components include the upper wing 103, lower wing 104, pylon 105,rudder 106, overhead boom 107, main landing gear pad 108, forward upperlift rotor 109, forward lower lift rotor 110, lift and push rotor 111,horizontal and vertical stabilizer 112, elevator 117 and aileron 118.

FIG. 5 shows the embodiment of box-wing multirotor vehicle 100 in VTOLconfiguration. The side view shows the tiltable lift and push rotor 111aiming at the downward direction to provide lift thrust. In detail, amechanical system pivots the tiltable lift and push rotor 111 relativesto the overhead boom 107. Furthermore, in VTOL configuration, lift rotor109, 110, 114 and 115 are powered to provide lift thrust.

FIG. 6 . shows the side view of the embodiment of the yaw servo tailboom 113. Advantageously, the yaw servo tail boom 113 acts as aredundant flight control to assist the vehicle to change yaw heading. Indetail, the yaw servo tail boom is mechanically coupled to the tail ofthe fuselage base 102. A rotating movement is applied to turn the yawservo tail boom 113 on its own axis of rotation 119. As a result, theyaw servo tail boom 113 rotates around the roll axis relative to thefuselage base 102, therefore thrust is directed sideway to yaw thevehicle.

The operation of the box-wing multirotor vehicle 100 is descried in thefollowing sections. Firstly, the box-wing multirotor vehicle 100operates in the VTOL mode for taking-off, landing, hovering, and flyingvertically. Secondly, the box-wing multirotor vehicle 100 operates inthe fixed wing airplane mode for forward flight.

Advantageously in the VTOL mode, a plurality of independent electricalmotors provides rotary movement to lift rotor 109, 110, 114 and 115. Asa result, lift thrust is generated by the spinning lift rotor 109, 110,114 and 115. Naturally, the lift forces propel the vehicle totaking-off, landing, hovering and flying vertically. Moreover, amechanical system permits the tiltable lift and push rotor 111 to aimdownward, therefore the produced thrust is also used for VTOL mode. Theusage of tiltable lift and push rotor 111 is optional to increase thecapacity of take-off payload or acts as redundant lift rotor. Firstly,the balance of thrust longitudinally and transversally allows thevehicle to fly levelly up and down in the Z axis. Secondly, an unbalanceof thrust longitudinally allows the vehicle to pitch forward or aft,which allows the vehicle to fly forward and aftward. Finally, anunbalance of thrust transversally allows the vehicle to roll sideward,which allows the vehicle to fly side way. Optionally, the yaw servo tailboom 113 acts as a redundant flight control to assist the vehicle tochange yaw heading.

Naturally, the torque effect of the rotor causes the vehicle to turn inthe opposite direction of the rotor's spin. The lift rotor spins aroundthe vertical axis, consequently the torque effect turns the yaw headingof the vehicle. Moreover, the magnitude of torque effect is proportionalto the thrust produced by the rotor. In the case of the contra-rotatinglift rotor, the torque effect is canceled out within everycontra-rotating lift rotor. The dual lift and push rotors 111 arerotating in the opposite direction, therefore the torque effect is alsocancelled out. As result, the vehicle maintains no yaw movement. In oneaspect, the yaw heading adjustment is accomplished by increasing thethrust to the lift rotor spinning in one direction and reducing thethrust of the lift rotor spinning in the opposite direction. Theunbalance of torque effect assists the vehicle to change yaw heading.

The operation of the box-wing multirotor vehicle 100 in airplane modefor forward flight is described in the following section. Firstly, afterairborne, thrust produced by the tiltable lift and push rotor 111 isredirected to aim at the aftward direction, to propel the vehicle to theforward direction. Finally, until a cruising speed is reached, liftrotor 109, 110, 114 and 115 becomes unpowered, and the lift to maintainthe vehicle airborne is provided solely by the wings. During airplanemode, the blade of lift rotor 109, 110, 114 and 115 are stowed inparallel with the longitudinal axis to reduce aerodynamic drag.Furthermore, the rudder 106, elevator 117 and aileron 118 provide theflight control capability to steer the vehicle in the pitch, roll andyaw axis. Moreover, horizontal and vertical stabilizer 112 providesdirectional stability for the vehicle.

FIG. 7 , illustrates the embodiment of the detachable cabin 101separated from box-wing multirotor vehicle 100. Firstly, in one aspect,a rail system between the detachable cabin 101 and fuselage base 102allows the detachable cabin 101 to slide out from fuselage base 102.Secondly, upon separating from the fuselage base 102, the detachablecabin 101 can be to be loaded on the flat bed of a specialized groundcar 120. As a result, this feature allows the payload to be hauled tothe final destination without being unloaded from the detachable cabin101. Advantageously, it allows quick change of payload between flight.The multirole cabin can accommodate payload such as passenger, cargo,energy storage and airborne equipment, but not limited to the describedpayload.

As shown in FIGS. 8 to 10 , the second embodiment of box-wing multirotor800 with an alternative lift rotor and push rotor configuration. In theusual way, the fuselage of the box-wing multirotor vehicle 800 comprisesof a detachable cabin 801 and the fuselage base 802. The upper portionof the fuselage base 802 is provided with upper wing 803 and the lowerportion of the fuselage base 802 is provided with lower wing 804.(Reference to FIG. 10 ) The upper wing 803 and lower wing 804 are joinedat the tip by the pylon 805. On the upper portion of the pylon 805 isprovided with the overhead boom 807. The pylon 805 is provided with acontrol rudder 806. On the lower portion of the pylon 805 is providedwith the main landing gear pad 808. It can also be the landing wheel.The forward portion of the overhead boom 807 is provided with theforward contra-rotating lift rotor, which comprises of the forward upperlift rotor 809 and forward lower lift rotor 810, and it may possibly beducted fan. The rear portion of the overhead boom 807 is provided withrear contra-rotating lift rotor, which comprises of the rear upper liftrotor 814 and rear lower lift rotor 815, and it may possibly be ductedfan. In the rear portion of the fuselage base 802 is provided with thehorizontal and vertical stabilizer 812. The tail portion of the fuselagebase 802 is provided with a push rotor 811, and it may possibly beducted fan. Push rotor 811 can also be co-axial rotor. At the noseportion of the fuselage base 802 is provided with nose landing gear pad816. It can also be the landing wheel. FIG. 10 shows the plane view ofthe embodiment. The wing of multirotor vehicle 800 comprises of thearticulated upper wing 803 sweeps forward from the top portion of thefuselage base 802. The upper wing 803 is provided with elevator 817. Thearticulated lower wing 804 sweeps aftward from the lower portion of thefuselage base 802. The lower wing 804 is provided with aileron 818.

The operation of the box-wing multirotor vehicle 800 is described in thefollowing sections. The box-wing multirotor vehicle 800 effectively hasfour dedicated contra-rotating lift rotors operating in the VTOL mode.Firstly, the quad contra-rotating lift rotors provide the lift thrust tobox-wing multirotor vehicle 800 to operate in VTOL mode for taking-off,landing, hovering, and flying vertically. Moreover, the torque effect ofthe rotors assists the vehicle to change yaw heading. Secondly, in thefixed wing airplane mode, the push rotor 811 propels the vehicle forwardto generate lift from the wings. Finally, until a cruising speed isreached, lift rotor 809, 810, 814 and 815 becomes unpowered, and thelift to maintain the vehicle airborne is provided solely by the wings.During airplane mode, the blade of the lift rotor 809, 810, 814 and 815are stowed in parallel with the longitudinal axis to reduce aerodynamicdrag. Furthermore, the rudder 806, elevator 817 and aileron 818 providethe flight control capability to steer the vehicle in the pitch, rolland yaw axis. Moreover, horizontal and vertical stabilizer 812 providesdirectional stability in forward flight mode.

Naturally, there are numerous variations, modifications andconfigurations which may be made hereto without departing from the scopeof the disclosure invention. It should be understood that theembodiments are for illustrative and explanatory purpose and it is notconceivable to identify exhaustively all possible embodiments. Inparticular, it is important to observe that the invention as describedrelates in particular to an aerial multirotor vehicle with lift rotorssecured to the box-wing. The design of the box-wing benefits from animprovement of structural strength, fatigue strength and load carryingstrength. The box-wing permits the lift rotors to be secured to theupper portion of the vehicle, which prevents the rotating blade fromstriking a person or object near the ground. Finally, the box-wing witha plurality of main wings design permits the wing span to be reduced inthe transverse direction. Nevertheless, the invention is applicable toany multirotor vehicle of arbitrary weight, such as a light drone to alarge tonnage vehicle.

1. A box-wing multirotor aerial vehicle adapted for VTOL comprising: adetachable cabin; a fuselage base, said fuselage base comprising: a noseportion; a lower portion; an upper portion; a rear portion; and a tailportion; a fixed box-wing, said fixed box wing comprising: a port sidefixed box-wing section, said port side fixed wing comprising: a staggerbiplane arrangement consisting of the transversally extended port sideupper wing secured to said upper portion of said fuselage base; and thetransversally extended port side lower wing secured to said lowerportion of said fuselage base; wherein said port side upper wing andsaid port side lower wing are spaced apart longitudinally andvertically; wherein said port side upper wing and said port side lowerwing have an articulated swept on the vertical and horizontal direction;wherein said port side upper wing and said port side lower wing arejoint at the tip by the port side pylon; a starboard side fixed box-wingsection, said starboard side fixed wing comprising: a stagger biplanearrangement consisting of the transversally extended starboard sideupper wing secured to said upper portion of said fuselage base; and thetransversally extended starboard side lower wing secured to said lowerportion of said fuselage base; wherein said starboard side upper wingand said starboard side lower wing are spaced apart longitudinally andvertically; wherein said starboard side upper wing and said starboardside lower wing have an articulated swept on the vertical and horizontaldirection; wherein said starboard side upper wing and said starboardside lower wing are joint at the tip by the starboard side pylon; a portside rudder is disposed on said port side pylon; a starboard side rudderis disposed on said starboard side pylon; a port side elevator isdisposed on said port side upper wing; a starboard side elevator isdisposed on said starboard side upper wing; a port side aileron isdisposed on said port side lower wing; a starboard side aileron isdisposed on said starboard side lower wing; a port side overhead boom,said port side overhead boom comprising: a middle portion secured to atleast one or more of said port side upper wing, said starboard sidelower wing, and said starboard side pylon; a forward portion is mountedwith the port side forward contra-rotating lift rotor; a rear portion ismechanically coupled to the port side tiltable lift and push rotor; astarboard side overhead boom, said starboard side overhead boomcomprising: a middle portion secured to at least one or more of saidstarboard side upper wing, said starboard side lower wing, and saidstarboard side pylon; a forward portion is mounted with the starboardside forward contra-rotating lift rotor; a rear portion is mechanicallycoupled to the starboard side tiltable lift and push rotor; a port sidemain landing gear pad and wheel secured to said port side pylon; astarboard main landing gear pad and wheel secured to said starboard sidepylon; a horizontal and vertical stabilizer comprising of at least oneor more of fixed horizontal airfoil, fixed vertical airfoil, fixeddiagonal airfoil and hinged flight control surface respectively securedon opposing sides of said rear portion of said fuselage base; a yawservo tail boom is mechanically coupled to said tail portion of saidfuselage base; a rear contra-rotating lift rotor mounted to said yawservo tail boom; a landing gear pad and wheel secured to said noseportion of said fuselage base;
 2. A box-wing multirotor vehicle as setforth in claim 1, wherein said detachable cabin is separable from saidbox-wing multirotor vehicle by sliding on an integrated rail system tobe loaded on a ground transportation device.
 3. A box-wing multirotorvehicle as set forth in claim 1, wherein the detachable cabin having theusage to hold passenger, cargo, equipment and energy storage.
 4. Abox-wing multirotor vehicle as set forth in claim 1, wherein said portside forward contra-rotating lift rotor, said starboard side forwardcontra-rotating lift rotor, and said rear contra-rotating lift rotorexert taking-off, landing, hovering and flying vertically lift, and yawheading torque effect.
 5. A box-wing multirotor vehicle as set forth inclaim 1, wherein said port side and starboard side tiltable lift andpush rotor aiming in the downward position exerts secondary lift neededfor take-off, for landing, for hovering, for flying vertically.
 6. Abox-wing multirotor vehicle as set forth in claim 1, wherein said portside and starboard side tiltable lift and push rotor aiming in theaftward position provides the propulsive force for forward motion.
 7. Abox-wing multirotor vehicle as set forth in claim 1, wherein said fixedbox-wing provides lift during forward flight.
 8. A box-wing multirotorvehicle as set forth in claim 1, wherein said rudders, elevators andailerons provide pitch, roll and yaw control during forward flight.
 9. Abox-wing multirotor vehicle as set forth in claim 1, wherein said fixedbox-wing having a triplane arrangement comprising of at least one ormore of articulated wings of aftward swept, the articulate wings offorward swept and the wings of straight swept.
 10. A box-wing multirotoraerial vehicle adapted for VTOL comprising: a detachable cabin; afuselage base, said fuselage base comprising: a nose portion; a lowerportion; an upper portion; a rear portion; and a tail portion; a fixedbox-wing, said fixed box wing comprising: a port side fixed box-wingsection, said port side fixed wing comprising: a stagger biplanearrangement consisting of the transversally extended port side upperwing secured to said upper portion of said fuselage base; and thetransversally extended port side lower wing secured to said lowerportion of said fuselage base; wherein said port side upper wing andsaid port side lower wing are spaced apart longitudinally andvertically; wherein said port side upper wing and said port side lowerwing have an articulated swept on the vertical and horizontal direction;wherein said port side upper wing and said port side lower wing arejoint at the tip by the port side pylon; a starboard side fixed box-wingsection, said starboard side fixed wing comprising: a stagger biplanearrangement consisting of the transversally extended starboard sideupper wing secured to said upper portion of said fuselage base; and thetransversally extended starboard side lower wing secured to said lowerportion of said fuselage base; wherein said starboard side upper wingand said starboard side lower wing are spaced apart longitudinally andvertically; wherein said starboard side upper wing and said starboardside lower wing have an articulated swept on the vertical and horizontaldirection; wherein said starboard side upper wing and said starboardside lower wing are joint at the tip by the starboard side pylon; a portside rudder is disposed on said port side pylon; a starboard side rudderis disposed on said starboard side pylon; a port side elevator isdisposed on said port side upper wing; a starboard side elevator isdisposed on said starboard side upper wing; a port side aileron isdisposed on said port side lower wing; a starboard side aileron isdisposed on said starboard side lower wing; a port side overhead boom,said port side overhead boom comprising: a middle portion secured to atleast one or more of said port side upper wing, said port side lowerwing, and said port side pylon; a forward portion is mounted with theport side forward contra-rotating lift rotor; a rear portion is mountedwith the port side rear contra-rotating lift rotor; a starboard sideoverhead boom, said starboard side overhead boom comprising: a middleportion secured to at least one or more of said starboard side upperwing, said starboard side lower wing, and said starboard side pylon; aforward portion is mounted with the starboard side forwardcontra-rotating lift rotor; a rear portion is mounted with the starboardside rear contra-rotating lift rotor; a port side main landing gear padand wheel secured to said port side pylon; a starboard main landing gearpad and wheel secured to said starboard side pylon; a horizontal andvertical stabilizer comprising of at least one or more of fixedhorizontal airfoil, fixed vertical airfoil, fixed diagonal airfoil andhinged flight control surface respectively secured on opposing sides ofsaid rear portion of said fuselage base; a push rotor secured to saidtail portion of said fuselage base; a landing gear pad and wheel securedto said nose portion of said fuselage base;
 11. A box-wing multirotorvehicle as set forth in claim 10, wherein said detachable cabin isseparable from said box-wing multirotor vehicle by sliding on anintegrated rail system to be loaded on a ground transportation device.12. A box-wing multirotor vehicle as set forth in claim 10, wherein thedetachable cabin having the usage to hold passenger, cargo, equipmentand energy storage.
 13. A box-wing multirotor vehicle as set forth inclaim 10, wherein said port side forward contra-rotating lift rotor,said starboard side contra-rotating lift rotor, said port side rearcontra-rotating lift rotor, and said starboard rear contra-rotating liftrotor exert taking-off, landing, hovering and flying vertically lift,and yaw heading torque effect.
 14. A box-wing multirotor vehicle as setforth in claim 10, wherein said push rotor provides the propulsive forcefor forward motion.
 15. A box-wing multirotor vehicle as set forth inclaim 10, wherein said push rotor is tiltable to aim downward to providelift thrust.
 16. A box-wing multirotor vehicle as set forth in claim 10,wherein said fixed box-wing provides lift during forward flight.
 17. Abox-wing multirotor vehicle as set forth in claim 10, wherein saidrudders, elevators and ailerons provide pitch, roll and yaw controlduring forward flight.
 18. A box-wing multirotor vehicle as set forth inclaim 10, wherein said fixed box-wing having a triplane arrangementcomprising of at least one or more of articulated wings of aftwardswept, the articulate wings of forward swept and the wings of straightswept.